Spacecraft motion control on the geostationary orbit using electrical thruster

The paper considers the problems of electrical thruster (ET) integration with a geostationary spacecraft (SC) based on the experience of the electropropulsion system application on the 'Meteor', 'Resurs', and 'GOMS' series sp acecraft. The technological procedures of the SPT integration with SC and the results of the SPT interaction with SC systems in space are also presented. The characteristics of the unique electroheating thruster being utilized for the 'GOMS' SC attitude control system and EW orbit correction are analyzed. The specific features of the SC control and its motion hold on geostationary orbit in all six DOF are considered, and a scheme for SC integration with a second-generation plasma thruster with the capability to control the thruster vector direction and value is proposed. The physical and mathematical model of the operation process in such a thruster is discussed. Results are presented for the electropropulsion system parameters optimization during its integration with SC having different masses, operation time, and types of construction layout of the thrusters on space platforms. (Author)